The structure of the initial system is calculated according to the aberration theory, in which the radius of the primary mirror is 300 mm, the radius of the secondary mirror is 320 mm, the distance between the primary mirror and the secondary mirror is 90 mm, and the blocking ratio is close to 0.4, and the occlusion ratio is close to 0.4. A three-piece correction lens set is designed to solve the spherical aberration and comet aberration caused by the Cassegrain system in the large field of view, and the imaging of the edge field of view of the large field of view system is realized. Through the optimization and layout of the overall system, the MTF value of the system is finally greater than 0.4 within the frequency of 130 lp/mm. This paper provides important reference value for the design of catadioptric optical system with large aperture and large field of view.
High-speed aircraft is very important for space safety and scientific exploration. When aircraft flies in near space at high speed, thin atmosphere outside aircraft forms high-speed convection. For optical detection device, the convection will cause aero optical effect, which can seriously affect the detection range and sensitivity of remote sensing system. In order to discuss the impact of aero optical effect for infrared detection device, we study the formation mechanism of aero optical effect and analyze the model of radiation transmission. Through static window heating test and dynamic flow field wind tunnel test, we verify the thermal radiation influence of quartz window and high-speed flow filed for short wave infrared detection system. The experimental results show that for 900nm-1700nm short wave infrared imaging system, short wave infrared signal of target can filter through quartz window below its melting point temperature. By accurately controlling exposure time, the thermal radiation effect of high-speed flow field can be weakened, and the target contrast can be improved for infrared detection system.
With the rapid increase of the number of spacecrafts, the space environment is becoming more and more complex. The demand of spacecraft for omni-directional detection of surrounding objects is becoming more and more urgent. This paper introduces a distributed space objects detection technology based on optical fiber image bundles. The system adopts multi aperture optical system. The optical signal is transmitted to the high-sensitivity image sensor through the fiber image bundle for imaging. Compared with the traditional method, the multi aperture optical system using fiber image bundles can be flexibly arranged according to the needs. The system has the advantages of wide field of view, flexible layout and low cost. This paper introduces the relevant technologies used and the principle prototype developed.
Mid-wave infrared imaging has the advantages of all day, high resolution, strong adaptability to the environment, so it is widely used. In high-speed target tracking and aiming. The target flying speed is extremely fast and the DOF (depth of field) of the fixed focal lens is limited, so the zoom lens is required. In order to ensure that the tracking target will not be lost, a fast zoom requirement of no more than 0.3s is proposed. According to the requirements, a compact athermalized mid-wave infrared dual field fast zoom lens is designed. The focal length is 400 mm and 200 mm, and the passive athermalization design is adopted which can meet the working temperature of - 40° to + 60°. the lens can match the cooling detector with effective pixel of 640 × 512, size of 15 μm and F/4 .The volume of the detector can be controlled in the range of L (196mm) × w (116mm) × H (185mm). The zoom group structure is considered in the design, and the switching time is less than 0.12s, and the image plane is stable when the zoom group switching.
Aiming at the threats to spacecraft safety caused by space debris, and improving the stability and working life of spacecraft in orbit, it is proposed to use spacecraft equipped with a safety self-perceptual optical payload to detect space debris to improve the safety of the aircraft in orbit. This paper analyses the application methods and characteristics of the safety self-perceptual optical payload of space vehicles, and defines the technical indicators of the optical payload. The safety self-Perceptual optical payload includes the MWIR optical system with large field of view and the visible continuous zoom lens with large zoom ratio. The detector resolution is 1280×1024, the pixel size is 15μm, the focal length is 8mm, the F number is 2, and the field of view is 97.6°×85° of MWIR optical system;The detector resolution is 1920×1080, the pixel size is 5.5μm, the focal length is 15mm~750mm, which has a 50 times zoom ratio, and the field of view is 38.8°×22.4°~0.80°×0.45° of the visible continuous zoom lens. The two systems are athermal designed in the temperature range of -40°C~60°C respectively to meet the environmental requirements of space applications. Safety self-perceptual optical payload could obtain, and apperceive long-range targets in the 10km range around the space vehicle, and improve the aircraft's survival ability
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